우주발사체 액체추진기관 시스템 해석

초록

In this study, space launch vehicle liquid propulsion system analysis and optimization program has been developed for suggesting the basis of minimum launch vehicle initial weight which satisfy mission velocity and altitude. The liquid propulsion analysis program has been developed using module programs of each part such as main thrust chamber, gas-generator, turbo-pump and turbines. Using a genetic algorithm, optimization program has been designed to find the minimum weight of the launch vehicle within a range of design variables. As the program execution results, 8~10% launch vehicle weight reduction has been estimated compared to existing launch vehicle, and it has been possible to obtain the variables about thrust geometry, turbo-pump power, gas-generator mass flow rate. This program is expected to be adopted in launch vehicle conceptual design process to find most efficient design.